Aircraft



Oct, 24, 1939. SCHAIRER 2,177,499

AIRCRAFT Filed March 3, 1937 6 Sheets-Sheet l fat M INVENTOR 6'50. 5.SCI/4W6? BY I'M/W ATTORNEY AIRCRAFT Filed March 3, 1937 6 Sheets-Sheet 2INVENTO'R Oct. 24, 1939. G. s. SCHAIRER AIRCRAFT Filed March 3, 1957 6Sheets-Sheet 3 INVENTOR 5 smwefe BY M W ATTORNEY Oct. 24, 1939. R2,177,499

AIRCRAFT Filed March 5, 1937 6 Sheets-Sheet 4 INVENTOR 6:0 5 SCI/W95?ATTORN EY Oct; 24, 1939. v G. s. SCHAIRER 2,177,499

A IRCRAFT Filed March 3, 1937 6 Sheets-Sheet 5 NNNNNN OR 6'50. .550/4/55? BY [J ATTORNEY Oct. 24, 1939. s, $HA|RER 2,177,499

AIRCRAFT Filed March 3, 1937 6 Sheets-Sheet 6 INVENTOR 6150. 5 5090/65?ATTORNEY Patented Oct. 24, .1939

AIRCRAFT George S. Schairer, South Bend, Ind., assignorto BendixProducts Corporation, South Bend; Ind., a corporation of IndianaApplication March 3, 1937, Serial No. 128,722

3 Claims.

This invention relates to aircraft, and more particularly to means for.fabricating aircraft economically.

Aircraft as constructed in the past have been subject to certainobjectionable characteristics, particularly inthat they have not beendesigned in such a manner that they could be fabricated economicallyfrom materials designed to provide adequate strength to protect thepilot and passengers without increasing the weight of the aircraftstructure more than was desirable in that type of craft.

An object of this invention is to providean aircraft, incorporatingcertain novel constructional details, which may be manufacturedeconomically.

Another object of the invention is to provide an aircraft fuselagehaving a metallic section forming passenger and engine compartments,

and a fabricated section including the control members operablyconnected to the metallic section. I A further object of the inventionis to form a metal and plywood fuselage wherein the engine is positionedbehind the passenger compartment. A still further object of theinvention isto provide an aircraft fuselage wherein an air-cooled engineis positioned behindthe passenger compartment, and air for coolingpurposes is admitted at the front of the fuselage and directed under thepassenger compartment to the engine. Yet a further object of theinvention is to provide an airplane fuselage wherein the for- Yet astill further object of the inventionis' to provide a metallic fuselagestructure wherein a single formed sheet metal frame may be employed toform the rounded corners of the fuselage, and substantially flat platesmay be employed to complete the fuselage structure,

A further object is to provide a fuselage structure wherein a metallicbox type forward section is provided to house passenger and enginecompartments, and wherein the rear section of the fuselage is formed asa 'unitary molded structure'which may be removed from the forward wardportion of the fuselage is formed of metal section to gain access to theengine positioned behind the passenger compartment.

Another object of the invention is to provide novel cooling means for anair-cooled aircraft engine which comprises admitting air to the fuselageat the forward end thereof and directing the air beneath the passengercompartment to cool the engine positioned behind the passengercompartment, and drawing the air out of the engine compartment by meansof a sirocco blower driven by the drive shaft of the engine.

A stillfurther object of the invention is to provide novel stabilizingand landing gear means wherein the wheels of the landing gear arestreamlined with reference to generally vertically disposed members ofthe stabilizing means.

A further object of the invention is to provide novel means forsupporting a stabilizing ring on a fuselage to increase the efliciencyof the propeller and also act as stabilizing surfaces.

Yet a further object is to provide a novel wing structure wherein ametallic nose section formed of reinforced sheet metal fabricated in anovel manner, and a fabric covered rear section are employed.

Another object of the invention is to provide a streamlined rearfuselage section formed of molded material.

A further object is to form a fuselage section of plywood.

Yet a still further object of the invention is to provide novelreinforcing means for sheet metal segments used in aircraftconstruction.

Other objects and advantages of this invention will be apparent from thefollowing detailed description of several illustrative embodiments,considered in connection with the accompanying drawings submitted forpurposes of illustration only and not intended to define the scope ofthe invention, reference being had for that purpose to the subjoinedclaims. y

In the drawings, wherein similar reference numerals have been applied tocorresponding parts:

Figure 1 is a side elevation of an aircraft emof flow of cooling air;

Figure 6 is a view taken on the line 6-6 of Figure 3;

Figure 7 is a view taken on the line 11-! of Figure 6;

Figure 8 is a view similar to Figure 1,- showing a modified form of theinvention;

Figure 9 is a front elevation of the aircraft shown in Figure 8;

Figure 10 is a View taken on the line Ill-l of Figure 8;

Figure 11 is a vertical section of the fuselage shown in Figures 8 and 9showing the direction Figure 12 is a side elevation blower shown inFigure 11;

Figure 13 is a perspective view, partly in section of a further modifiedform of the invention;

Figure 14 is a .view taken on the line l4-I4 of Figure 13 Figure 15 is aperspective view of a novel wing embodied within the present invention;

Figure 16 is a side elevation of a rib shown in Figure 15;

Figure 17 is a plan view of the rib shown in Figure 16; a

Figure 18 is an enlarged view of the upper nose structure shown inFigure 16; and

Figure 19 is an enlarged view of the lower nose structure shown inFigure 16.

The embodiment of the invention shown in Figures 1 to 7 has beenillustrated as applied to an aircraft of the rotary wing type.

In this embodiment the aircraft fuselage 8 is formed in two sections, aforward section l0, preferably formed of metal, and a rear section l2,preferably formed of plywood or molded material.

The forward-section ill of the fuselage is provided with a pair ofspaced landing wheels I4, and the rear section is provided with;a singlelanding wheel l6.

As more clearly shown in Figure 3, the forward section III isproportioned to form a passenger compartment I8 having windows I9 and ofthe .sirocco doors 2|, and an engine compartment 28 adapted to receivean air' cooled engine 22. The engine 22 -is operably connected, througha gear box 24 to drive a forwardly directed generally horizontallydisposed shaft 26, having a generally vertically disposed propeller 28fixed thereto. The gear box 24 is also designed to transmit power fromthe engine 22 to drive a generally vertically disposed shaft 30, havinggenerally horizontally disposed rotatable wings 32 fixed thereto.

The forward fuselage section III is formed of metallic sheets 34, fixedtogether in any desired .manner, as by welding. The metallic sheets 34are curved to form a streamlined structure as more clearly shown inFigures 3 and 5.

Reinforcing means including a generally horizontally disposed sheet ofmetal 36 extends across the bottom of the fuselage and is fixed to thesheets 34 in any desired manner, such, for example, as by welding, asmore clearly shown in Figure 5. The reinforcing sheet 36 forms thebottom of the passenger compartment l8. Extension of the floor boardsheet 36 at its forward and rearward ends as at 38 and 40 form thetoe-board and back of the passenger compartment respectively. It shouldbe noted that the reinforcing sheet 36 and its extensions 38 and 48cooperate with the outer shell sheets 34 forming an air passage in thfuselage section I0 and also provides a structure which is particularlystrong torsionally. It may also be noted that the floor sheet isreinforced at desired intervals with reinforcing channels 42.

The sheets 34 forming the outer shell of the fuselage may be reinforcedby the novel reinforcing segments shown on Figures 6 and 7. It

will be observed that channel shaped reinforcing segments 42 areprovided with attaching segments 44, which may be fixed to the sheets 34in any desired manner as by welding. A stiffening head 46 engaging theedge of the sheet 34 and the edge of the segments 44 reinforces thestructure at the windows 19 of the fuselage.

Air for cooling the engine 22 may be admitted through an aperture 48 inthe forward end of the fuselage section I8. The air is directed througha tunnel 50 under the passenger compartment l8 by the sheets 38 and 36respectively to the engine compartment 20. The air flows over the engineto cool it and is discharged from the compartment through louvres 52.

The rear section l2 of the fuselage may be formed as a unitary structureof plywood or molded material 54 adapted to be fastened to the frontsection ill to form the complete fuselage.

It will be observed that the tail wheel I6 is gral with the plywood ormolded material 54.

The front end' of the rear section 12 is provided with a metallic head82 having attaching lugs 64 fixed thereto embedded in the plywood ormolded material 54. -The lugs cooperate with, apertures 66 in the frontsection III to receive fastening means 68 to attach the front and rearsections l8 ,and l2 of the fuselage together.

It will be noted that a fuselage which is strong in the sectionsoccupied by the pilot or passengers is provided, yet the over-all weightof the craft is low since the rear section is extremely light. The rearsection, however, due to its shape, is adequately strong to withstandthe loads to which it is subjected.

To gain access to the engine compartment 28 to service the engine 22, itismerely necessary to jack up the rear portion of the front section It),remove the fastening means 68 andseparate the sections l0 and I2,whereupon full access to the engine 22'is permitted.

The embodiment of the invention shown in Figures 8 to 12has beenillustrated as applied This embodiment of the invention is illustratedas embodied in a fuselage 18 of the type wherein a single steerableforwardly disposed,

landing gear wheel 12 is employed, and a pair of spaced rearwardlydisposed landing gear wheels 14 are employed. The wheels 14 are carriedby and streamlined with reference to spaced generally verticallydisposed stabilizing surfaces 7 16. The vertically disposed stabilizingsurfaces shell 99, to the engine compartment 93.

16 are interconnected by means of generally hori-' zontally disposedstabilizing surfaces 18. The stabilizing surfaces 18 and 18 cooperate toprovide a directionally stable fuselage.

The upper ends of thevertically disposed stabilizing surfaces 16 areprovided with angularly disposed guide wires or struts 88, operablyconnected through yielding means 82 to the lower portion of the fuselage18, to permit vertical movement of the wheels 14 to act as shockabsorbing means between the fuselage l8 and the ground. Guide wires 84,connected to the lower portion of the vertically disposed stabilizingsurfaces 16,-and to the upper portion of the fuselage l8 prevent thewheels 14 from dropping below the desired operating position, whereinthe stabilizing surfaces 18 are positioned in a generally horizontallydisposed position, while the craft is in flight.

The fuselage 18 is operably connected to supporting wing means 88 bymeans of a pylon 88. The wing 86 may be oscillated vertically withreference to the fuselage 18 to control the craft longitudinally bymeans of a manually operable control member 88, and may be oscillatedabout the top of the pylon 85 to control the craft laterally.-

The fuselage I8 is of the type wherein a passenger compartment 98 ispositioned at the forward end. An engine 92, preferably of the invertedair-cooled type, is positioned in an engine compartment 93, at the rearend of the fuselage and drives a propeller 94 of the pusher type.

Air for cooling the engine 92 is admitted through an aperture 96 in theforward end of the fuselage l8 and is directed through a tunnel 98formed between an outer shell 99 of the fuselage, and a fuselagestiffening plate 91, welded or otherwise fixed to opposite sides of theouteAr blower 95, preferably of the sirocco type,'having air movingvanes 81 drivenby the engine 92, is positioned between the propeller 94and the engine 92. The air is directed by baflies 9| and 89 to flowbetween the cylinders and around the engine 92 to efiect adequatecooling.

The embodiment of the invention illustrated in Figures 13 and 14 issimilar in many respects to the embodiment illustrated in Figures 8 to'12, corresponding parts having therefore been given correspondingreference numerals with the addition of 100.

Inthis embodiment of the invention a relatively heavy formed sheet "9 ofany desired material may be stamped or otherwise shaped to form thelower rounded portion of the fuselage I18. The majority of the remainingportions of the fuselage may be formed from fiat sheets I" fastenedtogether in any desired manner as by welding. Some of the sheets, such,for example as the sheet I15 may be curved to conform to the desiredcontour ofthe fuselage I18.

A flat plate I13 may be fixed to the formed sheet I19 and to the sheetsill in any desired manner, as by welding, to form a floor for thepassenger compartment I98, and to stiffen the fuselage structuretorsionally.

A fuselage stabilizing ring I13 may be carried at the rear end of thefuselage to stabilize the craft both longitudinally and laterally. The

ring I13 is preferably positioned to surround the propeller |94 toincrease the efiiciency of the propeller. a

The ring I13 may be supported from the fuselage by means of angularlydisposed brace members Ill. The brace members I'll may, if desired, betapered outwardly, and streamlined to provide a morerigid structure andalso to assist I in stabilizing the craft. The brace members Illare'preferably formed from fiat sheets shaped to form streamlined strutmembers.

- Attention is directed to the fact that this embodiment of theinvention lends itself nicely to mass production, since substantiallyfiat plates angles 283 are disposed in such a manner that' their freeedges are directed toward the trailing edge of the wing. Generallyvertically disposed reinforcing angle members 281 are fixed to the fiatplate 285 by a riveting or welding operation to stiffen the spar 281. I

The wing is designed to employ a metallic leading edge 289 extendingover the spar 28l, toward the trailing edge of the wing, to the sectionsapproximately indicated by the points 2. metallic leading edge section289 is provided with longitudinally extending reinforcing angles 2|3welded or otherwise fixed thereto.

The nose rib is split into upper and lower sections 2|5 and 2|!respectively. The rib sections 2| 5 and 2 II are provided with flared orbent over sections 223 as more clearly shown in Figure 17 to stiffen therib. Slots 225 and indentations 221 are formed in the rib sections 2|5and 2 ll to receive the reinforcing angles 2| 3 carried by the metallicleading edge 289.

To assemble the wing the metallic leading edge 289 is welded orotherwise fixed to the rib sections 2|5 and 2| 1, the reinforcing angles2|3 carried by the section 289 fitting intothe slots 225 and theindentations 221. The upper and lower rib sections 2|5 and 2|! are thenrolled together and fastened by means of welding or riveting through theoverlapping sections 229.

The spar 28| is then placed in the leading section of the wing, the sparbeing in substantial abutment with the ends of the rib sections 2|5 and2". The rearwardly directed free edges of the angles 283 of the spar 28|and the forward portion of the rib section 23l,.forming the convergingsection of. the wing, are then fastened to the section 289 by a weldingor riveting operation.

.The converging section of the wing may be covered with any desiredmaterial, such, for example as fabric, plywood or metal.

Attention is directed to the fact that this wing design provides astructure which may be formed entirely by a welding or rivetingoperation as desired. The internal structural members may of course beapertured to decrease the weight of the wing. The wing structure isextremely strong, yet light.

While the invention has particular reference to several desirableembodiments, it is to be understood that the scope of the invention isnot to be limited by the constructional details shown and discussed,since many changes may be made without departing from the spirit of theinvention as defined by the following claims.

I claim:

The.

been described with 11 In an aircraft, a fuselage having a metal forwardportion having a forwardly directed air inlet and including a passengercompartment, an

engine compartment positioned behind the passenger compartmentfan aircooled engine in. the engine compartment, a generally horizontallydisposed surface forming a floor in the passenger compartment and spacedabove the bottom of the fuselage to strengthen the fuselage and toprovide an air directing passageway from the air inlet to the enginecompartment.

2. In an aircraft fuselage, a metallic forward portion having aforwardly disposed air inlet and including a passenger compartment, anengine compartment behind the passenger compartment, a generallyhorizontally disposed plate fixed in the fuselage above the bottomthereof to provide a floor in the passenger compartment and form a boxtype structure to strengthen the fuselage and to provide an airdirecting passageway beneath the floor of the passenger compartment todirect air to the engine compartment.

3. A metallic airplane fuselage including a passenger compartmentcomprising a plate shaped to form the curved forward and lower sectionsthereof, a plurality of substantially flat sheets fixed to said plate, areinforcing plate fixed to the shaped plate and the flat sheets andforming a floor and a back rest for the passenger compartment, an enginecompartment behind the passenger compartment, and means to admit air atthe forward end of the fuselage and transmit it to the enginecompartment beneath the floor of the passenger 15 compartment.

GEORGE S. SCHAIRER.

